Dynamically adjusting width of beam based on altitude

ABSTRACT

An antenna includes a radiator and a reflector and has a radiation pattern that is based at least in part on a separation distance between the radiator and the reflector. The antenna includes a linkage configured to adjust the separation distance based at least in part on the altitude of the antenna. The resulting radiation pattern can be dynamically adjusted based on altitude of the antenna such that, while the antenna is aloft and the antenna is ground-facing, variations in geographic boundaries and intensity of the radiation received at ground level are at least partially compensated for by the dynamic adjustments to the radiation pattern.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims priority to U.S. patent application Ser. No.13/892,161, filed May 10, 2013, entitled “Dynamically Adjusting Width ofBeam Based on Altitude”, now pending, the contents of which areincorporated by reference herein for all purposes.

BACKGROUND

Unless otherwise indicated herein, the materials described in thissection are not prior art to the claims in this application and are notadmitted to be prior art by inclusion in this section.

Computing devices such as personal computers, laptop computers, tabletcomputers, cellular phones, and countless types of Internet-capabledevices are increasingly prevalent in numerous aspects of modern life.As such, the demand for data connectivity via the Internet, cellulardata networks, and other such networks, is growing. However, there aremany areas of the world where data connectivity is still unavailable, orif available, is unreliable and/or costly.

SUMMARY

Example embodiments relate to a network of balloon-mounted ground-facingantennas for an aerial communication network. Balloons can be formed ofan envelope supporting a payload with a power supply, data storage, andone or more transceivers for wirelessly communicating information toother members of the balloon network and/or to wireless stations locatedon the ground.

Some embodiments of the present disclosure provide an antenna configuredto be mounted to a high altitude platform. The antenna can include aradiator, a reflector, and a linkage. The radiator can be configured toemit radiation according to a feed signal. The reflector configured todirect radiation emitted from the radiator such that reflected radiationis characterized by an emission pattern determined at least in part by aseparation distance between the radiator and the reflector. Thereflector can be configured to be situated such that the emissionpattern is directed in a ground-facing direction while the associatedhigh altitude platform is aloft. The linkage configured to adjust theseparation distance between the radiator and the reflector according toan altitude of the associated high altitude platform.

Some embodiments of the present disclosure provide a balloon. Theballoon can include an envelope, a payload configured to be suspendedfrom the envelope, and an antenna. The antenna can be mounted to thepayload and situated so as to be ground-facing while the balloon isaloft. The antenna can include: (i) a radiator configured to emitradiation according to feed signals; (ii) a reflector configured todirect the radiation emitted from the radiator according to a radiationpattern determined at least in part according to a separation distancebetween the radiator and the reflector; and (iii) a linkage configuredto adjust the separation distance between the radiator and the reflectoraccording to an altitude of the antenna.

Some embodiments of the present disclosure provide a method. The methodcan include emitting radiation from an antenna configured to be mountedto a payload of an associated balloon. The antenna can have an emissionpattern determined at least in part by a separation distance between aradiator and a reflector of the antenna. The antenna can be configuredto be situated such that the emission pattern is directed in aground-facing direction while the associated balloon is aloft and theantenna is mounted to the payload. The method can include decreasing theseparation distance between the radiator and the reflector responsive toa decrease in altitude of the associated balloon. The method can includeincreasing the separation distance between the radiator and thereflector responsive to an increase in altitude of the associatedballoon.

Some embodiments of the present disclosure provide means for emittingradiation from an antenna configured to be mounted to a payload of anassociated balloon. The antenna can have an emission pattern determinedat least in part by a separation distance between a radiator and areflector of the antenna. The antenna can be configured to be situatedsuch that the emission pattern is directed in a ground-facing directionwhile the associated balloon is aloft and the antenna is mounted to thepayload. Some embodiments can include means for decreasing theseparation distance between the radiator and the reflector responsive toa decrease in altitude of the associated balloon. Some embodiments caninclude means for increasing the separation distance between theradiator and the reflector responsive to an increase in altitude of theassociated balloon.

These as well as other aspects, advantages, and alternatives, willbecome apparent to those of ordinary skill in the art by reading thefollowing detailed description, with reference where appropriate to theaccompanying drawings.

BRIEF DESCRIPTION OF THE DRAWING

FIG. 1 is a simplified block diagram illustrating a balloon network,according to an example embodiment.

FIG. 2 is a block diagram illustrating a balloon-network control system,according to an example embodiment.

FIG. 3 is a simplified block diagram illustrating a high-altitudeballoon, according to an example embodiment.

FIG. 4A is a diagram of a balloon with a downward-facing antennasituated to illuminate a geographic region from a first elevation.

FIG. 4B is a diagram of the balloon in FIG. 4A illuminating thegeographic region from a second elevation.

FIG. 4C is a side view diagram of an antenna configured to illuminate abroad emission pattern.

FIG. 4D is a side view diagram of an antenna configured to illuminate anarrow emission pattern.

FIG. 5A is a simplified block diagram of an antenna with a dynamicallyadjustable emission pattern.

FIG. 5B is a simplified block diagram of another antenna with adynamically adjustable emission pattern.

FIG. 5C is a simplified block diagram of another antenna with adynamically adjustable emission pattern.

FIG. 6A shows a pressure-sensitive vessel in an expanded state.

FIG. 6B shows the pressure-sensitive vessel in a contracted state.

FIG. 7A is a simplified diagram of an antenna with a flat reflector.

FIG. 7B is a simplified diagram of another antenna with a flatreflector.

FIG. 8A is a flowchart of a process for dynamically adjusting an antennaemission pattern according to an example embodiment.

FIG. 8B is a flowchart of a process for dynamically adjusting an antennaemission pattern according to an example embodiment.

FIG. 9 illustrates a computer readable medium according to an exampleembodiment.

DETAILED DESCRIPTION

Example methods and systems are described herein. Any example embodimentor feature described herein is not necessarily to be construed aspreferred or advantageous over other embodiments or features. Theexample embodiments described herein are not meant to be limiting. Itwill be readily understood that certain aspects of the disclosed systemsand methods can be arranged and combined in a wide variety of differentconfigurations, all of which are contemplated herein.

1. Overview

Example embodiments relate to an aerial communication network using aplurality of balloons with communication equipment to facilitatewireless communication with ground-based stations and among theballoons. Balloons can be formed of an envelope supporting a payloadwith a power supply, data storage, and one or more transceivers forwirelessly communicating information to other members of the balloonnetwork and/or to wireless stations located on the ground. Tocommunicate with ground-based stations while aloft, the balloons can beequipped with antennas mounted to the balloon payload so as to beground-facing.

A ground-facing antenna can include a radiating element situated toradiate toward a reflector. The reflector may be a dish, such as aquasi-parabolic dish that may be spherically invariant. The radiatingelement can emit signals toward the reflector, which results inradiation emitted from the antenna with a directional emission pattern.The directional emission pattern can be approximated as a cone-shapedregion with an apex located near the antenna. The directivity of theemission pattern is thus determined by the breadth or narrowness of theregion illuminated by the emission pattern, and can be characterized byan opening angle of the conical surface bounding the illuminated region.The opening angle (and thus the antenna directivity) is determined, atleast in part, by the separation distance between the radiating elementand the reflector. Generally, a greater separation distance correspondsto a narrower emission pattern, whereas a lesser separation distancecorresponds to a broader emission pattern.

In some examples, the emission pattern can be adjusted as the balloonchanges altitude. For example, the radiating element in the antenna canbe moved closer or further from the reflector to dynamically adjust thewidth of the emission pattern based on the altitude of the balloon. Acontrol system can determine the altitude of the balloon and then causethe separation distance between the radiating element and the reflectorto be adjusted according to the determined altitude.

In some examples, a pressure-sensitive vessel that expands and contractsas the balloon changes altitude based on the atmospheric pressure can beincluded in a linkage that mounts the radiator and/or reflector to theballoon payload. The expansion and contraction of the vessel can thusexpand or contract or the linkage and thereby passively adjust theseparation distance as the altitude varies.

The emission pattern may be adjusted to account for variations in theemitted radiation at ground level due to altitude changes of theballoon. Such adjustments may be carried out to cause the width of theemission pattern at ground level to be substantially unchanged evenwhile the balloon altitude varies. Additionally or alternatively,adjustments may be carried out to cause the intensity of the emissionpattern at ground level to be substantially unchanged even while theballoon altitude varies.

Each of these specific methods and systems are contemplated herein, andseveral example embodiments are described below.

2. Example Systems

FIG. 1 is a simplified block diagram illustrating a balloon network 100,according to an example embodiment. As shown, balloon network 100includes balloons 102A to 102F, which are configured to communicate withone another via free-space optical links 104 (e.g., by sending andreceiving optical radiation encoded with data). Moreover, while referredto as “optical,” communication on the optical links 104 may be carriedout with radiation at a range of wavelengths including radiation outsidethe visible spectrum, such as infrared radiation, ultraviolet radiation,etc. Balloons 102A to 102F could additionally or alternatively beconfigured to communicate with one another via radio frequency (RF)links 114 (e.g., by sending and receiving radio frequency radiationencoded with data). Balloons 102A to 102F may collectively function as amesh network for packet-data communications. Further, at least someballoons (e.g., 102A and 102B) may be configured for RF communicationswith a ground-based station 106 via respective RF links 108. Further,some balloons, such as balloon 102F, could be configured to communicatevia optical link 110 with a suitably equipped ground-based station 112.

In an example embodiment, balloons 102A to 102F are high-altitudeballoons, which are deployed in the stratosphere. At moderate latitudes,the stratosphere includes altitudes between approximately 10 kilometers(km) and 50 km altitude above the surface of the Earth. At the poles,the stratosphere starts at an altitude of approximately 8 km. In anexample embodiment, high-altitude balloons may be generally configuredto operate in an altitude range within the stratosphere that hasrelatively low wind speed (e.g., between 8 and 32 kilometers per hour(kph)).

More specifically, in a high-altitude-balloon network, balloons 102A to102F may generally be configured to operate at altitudes between 18 kmand 25 km (although other altitudes are possible). This altitude rangemay be advantageous for several reasons. In particular, this altituderegion of the stratosphere generally has relatively desirableatmospheric conditions with low wind speeds (e.g., winds between 8 and32 kph) and relatively little turbulence. Further, while winds betweenaltitudes of 18 km and 25 km may vary with latitude and by season, thevariations can be modeled with reasonably accuracy and thereby allow forpredicting and compensating for such variations. Additionally, altitudesabove 18 km are typically above the maximum altitude designated forcommercial air traffic.

To transmit data to another balloon, a given balloon 102A to 102F may beconfigured to transmit an optical signal via an optical link 104. In anexample embodiment, a given balloon 102A to 102F may use one or morehigh-power light-emitting diodes (LEDs) to transmit an optical signal.Alternatively, some or all of balloons 102A to 102F may include lasersystems for free-space optical communications over optical links 104.Other types of free-space optical communication are possible. Further,in order to receive an optical signal from another balloon via anoptical link 104, a given balloon 102A to 102F may include one or moreoptical receivers.

In a further aspect, balloons 102A to 102F may utilize one or more ofvarious different RF air-interface protocols for communication withground-based stations 106 and 112 via respective RF links 108. Forinstance, some or all of balloons 102A to 102F may be configured tocommunicate with ground-based stations 106 and 112 using protocolsdescribed in IEEE 802.11 (including any of the IEEE 802.11 revisions),various cellular protocols such as GSM, CDMA, UMTS, EV-DO, WiMAX, and/orLTE, and/or one or more propriety protocols developed for balloon-groundRF communication, among other possibilities.

In a further aspect, there may be scenarios where RF links 108 do notprovide a desired link capacity for balloon-to-ground communications.For instance, increased capacity may be desirable to provide backhaullinks from a ground-based gateway, and in other scenarios as well.Accordingly, an example network may also include one or more downlinkballoons, which could provide a high-capacity air-ground link to connectthe balloon network 100 to ground-based network elements.

For example, in balloon network 100, balloon 102F is configured as adownlink balloon. Like other balloons in an example network, thedownlink balloon 102F may be operable for optical communication withother balloons via optical links 104. However, the downlink balloon 102Fmay also be configured for free-space optical communication with aground-based station 112 via an optical link 110. Optical link 110 maytherefore serve as a high-capacity link (as compared to an RF link 108)between the balloon network 100 and the ground-based station 112.

Note that in some implementations, the downlink balloon 102F mayadditionally be operable for RF communication with ground-based stations106. In other cases, the downlink balloon 102F may only use an opticallink for balloon-to-ground communications. Further, while thearrangement shown in FIG. 1 includes just one downlink balloon 102F, anexample balloon network can also include multiple downlink balloons. Onthe other hand, a balloon network can also be implemented without anydownlink balloons.

In other implementations, a downlink balloon may be equipped with aspecialized, high-bandwidth RF communication system forballoon-to-ground communications, instead of, or in addition to, afree-space optical communication system. The high-bandwidth RFcommunication system may take the form of an ultra-wideband system,which may provide an RF link with substantially the same capacity as oneof the optical links 104. Other forms are also possible.

Ground-based stations, such as ground-based stations 106 and/or 112, maytake various forms. Generally, a ground-based station may includecomponents such as transceivers, transmitters, and/or receivers forwireless communication via RF links and/or optical links withcorresponding transceivers situated on balloons in the balloon network100. Further, a ground-based station may use various air-interfaceprotocols to communicate with balloons 102A to 102F over an RF link 108.As such, ground-based stations 106 and 112 may be configured as anaccess point via which various devices can connect to balloon network100. Ground-based stations 106 and 112 may have other configurationsand/or serve other purposes without departing from the scope of thepresent disclosure.

In a further aspect, some or all of balloons 102A to 102F could beadditionally or alternatively configured to establish a communicationlink with space-based satellites. In some embodiments, a balloon maycommunicate with a satellite via an optical link. However, other typesof satellite communications are possible.

Further, some ground-based stations, such as ground-based stations 106and 112, may be configured as gateways between balloon network 100 andone or more other networks. Such ground-based stations 106 and 112 maythus serve as an interface between the balloon network and the Internet,a cellular service provider's network, and/or other types of networksfor communicating information. Variations on this configuration andother configurations of ground-based stations 106 and 112 are alsopossible.

2a) Mesh Network Functionality

As noted, balloons 102A to 102F may collectively function as a meshnetwork. More specifically, since balloons 102A to 102F may communicatewith one another using free-space optical links, the balloons maycollectively function as a free-space optical mesh network.

In a mesh-network configuration, each balloon 102A to 102F may functionas a node of the mesh network, which is operable to receive datadirected to it and to route data to other balloons. As such, data may berouted from a source balloon to a destination balloon by determining anappropriate sequence of optical links between the source balloon and thedestination balloon. These optical links may be collectively referred toas a “lightpath” for the connection between the source and destinationballoons. Further, each of the optical links may be referred to as a“hop” on the lightpath. Each intermediate balloon (i.e., hop) along aparticular lightpath may act as a repeater station to first detect theincoming communication via received optical signals and then repeat thecommunication by emitting a corresponding optical signal to be receivedby the next balloon on the particular lightpath. Additionally oralternatively, a particular intermediate balloon may merely directincident signals toward the next balloon, such as by reflecting theincident optical signals to propagate toward the next balloon.

To operate as a mesh network, balloons 102A to 102F may employ variousrouting techniques and self-healing algorithms. In some embodiments, theballoon network 100 may employ adaptive or dynamic routing, where alightpath between a source and destination balloon is determined andset-up when the connection is needed, and released at a later time.Further, when adaptive routing is used, the lightpath may be determineddynamically depending upon the current state, past state, and/orpredicted state of the balloon network 100.

In addition, the network topology may change as the balloons 102A to102F move relative to one another and/or relative to the ground.Accordingly, an example balloon network 100 may apply a mesh protocol toupdate the state of the network as the topology of the network changes.For example, to address the mobility of the balloons 102A to 102F,balloon network 100 may employ and/or adapt various techniques that areemployed in mobile ad hoc networks (MANETs). Other examples are possibleas well.

In some implementations, the balloon network 100 may be configured as atransparent mesh network. More specifically, in a transparent meshnetwork configuration, the balloons may include components for physicalswitching that are entirely optical, without any electrical componentsinvolved in the routing of optical signals. Thus, in a transparentconfiguration with optical switching, signals can travel through amulti-hop lightpath that is entirely optical.

In other implementations, the balloon network 100 may implement afree-space optical mesh network that is opaque. In an opaqueconfiguration, some or all balloons 102A to 102F may implementoptical-electrical-optical (OEO) switching. For example, some or allballoons may include optical cross-connects (OXCs) for OEO conversion ofoptical signals. Other opaque configurations are also possible.Additionally, network configurations are possible that include routingpaths with both transparent and opaque sections.

In a further aspect, balloons in the balloon network 100 may implementwavelength division multiplexing (WDM), which may be used to increaselink capacity. When WDM is implemented with transparent switching, itmay be necessary to assign the same wavelength for all optical links ona given lightpath. Lightpaths in transparent balloon networks aretherefore said to be subject to a “wavelength continuity constraint,”because each hop in a particular lightpath may be required to use thesame wavelength.

An opaque configuration, on the other hand, may avoid such a wavelengthcontinuity constraint. In particular, balloons in an opaque balloonnetwork may include OEO switching systems operable for wavelengthconversions along a given lightpath. As a result, balloons can convertthe wavelength of an optical signal at one or more hops along aparticular lightpath.

2b) Control of Balloons in a Balloon Network

In some embodiments, mesh networking and/or other control functions maybe centralized. For example, FIG. 2 is a block diagram illustrating aballoon-network control system, according to an example embodiment. Inparticular, FIG. 2 shows a distributed control system, which includes acentral control system 200 and a number of regional control-systems 202Ato 202B. Such a control system may be configured to coordinate certainfunctionality for balloon network 204, and as such, may be configured tocontrol and/or coordinate certain functions for balloons 206A to 206I.

In the illustrated embodiment, central control system 200 may beconfigured to communicate with balloons 206A to 206I via a number ofregional control systems 202A to 202C. These regional control systems202A to 202C may be configured to receive communications and/oraggregate data from balloons in the respective geographic areas thatthey cover, and to relay the communications and/or data to centralcontrol system 200. Further, regional control systems 202A to 202C maybe configured to route communications from central control system 200 tothe balloons in their respective geographic areas. For instance, asshown in FIG. 2, regional control system 202A may relay communicationsand/or data between balloons 206A to 206C and central control system200, regional control system 202B may relay communications and/or databetween balloons 206D to 206F and central control system 200, andregional control system 202C may relay communications and/or databetween balloons 206G to 206I and central control system 200.

In order to facilitate communications between the central control system200 and balloons 206A to 206I, certain balloons may be configured asdownlink balloons, which are operable to communicate with regionalcontrol systems 202A to 202C. Accordingly, each regional control system202A to 202C may be configured to communicate with the downlink balloonor balloons in the respective geographic area it covers. For example, inthe illustrated embodiment, balloons 206A, 206F, and 206I are configuredas downlink balloons. As such, regional control systems 202A to 202C mayrespectively communicate with balloons 206A, 206F, and 206I via opticallinks 206, 208, and 210, respectively.

In the illustrated configuration, only some of balloons 206A to 206I areconfigured as downlink balloons. The balloons 206A, 206F, and 206I thatare configured as downlink balloons may relay communications fromcentral control system 200 to other balloons in the balloon network,such as balloons 206B to 206E, 206G, and 206H. However, it should beunderstood that in some implementations, it is possible that allballoons may function as downlink balloons. Further, while FIG. 2 showsmultiple balloons configured as downlink balloons, it is also possiblefor a balloon network to include only one downlink balloon.

The regional control systems 202A to 202C may be particular types ofground-based stations that are configured to communicate with downlinkballoons (e.g., such as ground-based station 112 of FIG. 1). Thus, whilenot shown in FIG. 2, a control system may be implemented in conjunctionwith other types of ground-based stations (e.g., access points,gateways, etc.).

In a centralized control arrangement, such as that shown in FIG. 2, thecentral control system 200 (and possibly regional control systems 202Ato 202C as well) may coordinate certain mesh-networking functions forballoon network 204. For example, balloons 206A to 206I may send thecentral control system 200 certain state information, which the centralcontrol system 200 may utilize to determine the state of balloon network204. The state information from a given balloon may include locationdata, optical-link information (e.g., the identity of other balloonswith which the balloon has established an optical link, the bandwidth ofthe link, wavelength usage and/or availability on a link, etc.), winddata collected by the balloon, and/or other types of information.Accordingly, the central control system 200 may aggregate stateinformation from some or all of the balloons 206A to 206I in order todetermine an overall state of the network 204.

Based in part on the overall state of the network 204, the controlsystem 200 may then be used to coordinate and/or facilitate certainmesh-networking functions, such as determining lightpaths forconnections, for example. The central control system 200 may determine acurrent topology (or spatial distribution of balloons) based on theaggregate state information from some or all of the balloons 206A to206I. The topology may indicate the current optical links that areavailable in the balloon network and/or the wavelength availability onsuch links. The topology may then be sent to some or all of the balloonsso that individual balloons are enabled to select appropriate lightpaths(and possibly backup lightpaths) for communications through the balloonnetwork 204 as needed.

In a further aspect, the central control system 200 (and possiblyregional control systems 202A to 202C as well) may also coordinatecertain positioning functions for balloon network 204 to achieve adesired spatial distribution of balloons. For example, the centralcontrol system 200 may input state information that is received fromballoons 206A to 206I to an energy function, which may effectivelycompare the current topology of the network to a desired topology, andprovide a vector indicating a direction of movement (if any) for eachballoon, such that the balloons can move towards the desired topology.Further, the central control system 200 may use altitudinal wind data todetermine respective altitude adjustments that may be initiated toachieve the movement towards the desired topology. The central controlsystem 200 may provide and/or support other station-keeping functions aswell.

FIG. 2 shows a distributed arrangement that provides centralizedcontrol, with regional control systems 202A to 202C coordinatingcommunications between a central control system 200 and a balloonnetwork 204. Such an arrangement may be useful to provide centralizedcontrol for a balloon network that covers a large geographic area. Insome embodiments, a distributed arrangement may even support a globalballoon network that provides coverage everywhere on earth. Of course, adistributed-control arrangement may be useful in other scenarios aswell.

Further, it should be understood that other control-system arrangementsare also possible. For instance, some implementations may involve acentralized control system with additional layers (e.g., sub-regionsystems within the regional control systems, and so on). Alternatively,control functions may be provided by a single, centralized, controlsystem, which communicates directly with one or more downlink balloons.

In some embodiments, control and coordination of a balloon network maybe shared by a ground-based control system and a balloon network tovarying degrees, depending upon the implementation. In fact, in someembodiments, there may be no ground-based control systems. In such anembodiment, all network control and coordination functions may beimplemented by the balloon network itself (e.g., by processing systemssituated on payloads of one more balloons in the network 204). Forexample, certain balloons may be configured to provide the same orsimilar functions as central control system 200 and/or regional controlsystems 202A to 202C. Other examples are also possible.

Furthermore, control and/or coordination of a balloon network may bede-centralized. For example, each balloon may relay state informationto, and receive state information from, some or all nearby balloons.Further, each balloon may relay state information that it receives froma nearby balloon to some or all nearby balloons. When all balloons doso, each balloon may be able to individually determine the state of thenetwork. Alternatively, certain balloons may be designated to aggregatestate information for a given portion of the network. These balloons maythen coordinate with one another to determine the overall state of thenetwork.

Further, in some aspects, control of a balloon network may be partiallyor entirely localized, such that it is not dependent on the overallstate of the network. For example, individual balloons may implementballoon-positioning functions that only consider nearby balloons. Inparticular, each balloon may determine how to move (and/or whether tomove) based on its own state and the states of nearby balloons. Theballoons may use an optimization routine (e.g., an energy function) todetermine respective positions to, for example, maintain and/or move toa desired position with respect to the nearby balloons, withoutnecessarily considering the desired topology of the network as a whole.However, when each balloon implements such an position determinationroutine, the balloon network as a whole may maintain and/or move towardsthe desired spatial distribution (topology).

2c) Example Balloon Configuration

Various types of balloon systems may be incorporated in an exampleballoon network. As noted above, an example embodiment may utilizehigh-altitude balloons, which could typically operate in an altituderange between 18 km and 25 km. FIG. 3 illustrates a high-altitudeballoon 300, according to an example embodiment. As shown, the balloon300 includes an envelope 302, a skirt 304, and a payload 306, which isshown as a block diagram.

The envelope 302 and skirt 304 may take various forms, which may becurrently well-known or yet to be developed. For instance, the envelope302 and/or skirt 304 may be made of metallic and/or polymeric materialsincluding metalized Mylar or BoPet. Additionally or alternatively, someor all of the envelope 302 and/or skirt 304 may be constructed from ahighly-flexible latex material or a rubber material such as chloroprene.Other materials are also possible. The envelope 302 may be filled with agas suitable to allow the balloon 300 to reach desired altitudes in theEarth's atmosphere. Thus, the envelope 302 may be filled with arelatively low-density gas, as compared to atmospheric mixtures ofpredominantly molecular nitrogen and molecular oxygen, to allow theballoon 300 to be buoyant in the Earth's atmosphere and reach desiredaltitudes. Various different gaseous materials with suitable propertiesmay be used, such as helium and/or hydrogen. Other examples of gaseousmaterials (including mixtures) are possible as well.

The payload 306 of balloon 300 may include a computer system 312 havinga processor 313 and on-board data storage, such as memory 314. Thememory 314 may take the form of or include a non-transitorycomputer-readable medium. The non-transitory computer-readable mediummay have instructions stored thereon, which can be accessed and executedby the processor 313 in order to carry out the balloon functionsdescribed herein. Thus, processor 313, in conjunction with instructionsstored in memory 314, and/or other components, may function as acontroller of balloon 300.

The payload 306 of balloon 300 may also include various other types ofequipment and systems to provide a number of different functions. Forexample, payload 306 may include an optical communication system 316,which may transmit optical signals via an ultra-bright LED system, andwhich may receive optical signals via an optical-communication receiver(e.g., a photodiode receiver system). Further, payload 306 may includean RF communication system 318, which may transmit and/or receive RFcommunications via an antenna system.

The payload 306 may also include a power supply 326 to supply power tothe various components of balloon 300. The power supply 326 couldinclude a rechargeable battery or other energy storage devices. Theballoon 300 may include a solar power generation system 327. The solarpower generation system 327 may include solar panels and could be usedto generate power that charges and/or is distributed by the power supply326. In other embodiments, the power supply 326 may additionally oralternatively represent other means for producing power.

The payload 306 may additionally include a positioning system 324. Thepositioning system 324 could include, for example, a global positioningsystem (GPS), an inertial navigation system, and/or a star-trackingsystem. The positioning system 324 may additionally or alternativelyinclude various motion sensors (e.g., accelerometers, magnetometers,gyroscopes, and/or compasses). The positioning system 324 mayadditionally or alternatively include one or more video and/or stillcameras, and/or various sensors for capturing environmental dataindicative of the geospatial position of the balloon 300, whichinformation may be used by the computer system 312 to determine thelocation of the balloon 300.

Some or all of the components and systems within payload 306 may beimplemented in a radiosonde or other probe, which may be operable tomeasure environmental parameters, such as pressure, altitude,geographical position (latitude and longitude), temperature, relativehumidity, and/or wind speed and/or wind direction, among otherinformation.

As noted, balloon 300 may include an ultra-bright LED system forfree-space optical communication with other balloons. As such, opticalcommunication system 316 may be configured to transmit a free-spaceoptical signal by modulating the ultra-bright LED system. The opticalcommunication system 316 may be implemented with mechanical systemsand/or with hardware, firmware, and/or software. Generally, the mannerin which an optical communication system is implemented may vary,depending upon the particular application. The optical communicationsystem 316 and other associated components are described in furtherdetail below.

In a further aspect, balloon 300 may be configured for altitude control.For instance, balloon 300 may include a variable buoyancy system, whichis configured to change the altitude of the balloon 300 by adjusting thevolume and/or density of the gas in the balloon 300. A variable buoyancysystem may take various forms, and may generally be any system that canchange the volume and/or density of gas in the envelope 302.

In an example embodiment, a variable buoyancy system may include abladder 310 that is located inside of envelope 302. The bladder 310could be an elastic chamber configured to hold liquid and/or gas.Alternatively, the bladder 310 need not be inside the envelope 302. Forinstance, the bladder 310 could be a rigid container holding liquefiedand/or gaseous material that is pressurized in excess of the pressureoutside the bladder 310. The buoyancy of the balloon 300 may thereforebe adjusted by changing the density and/or volume of the gas in bladder310. To change the density in bladder 310, balloon 300 may be configuredwith systems and/or mechanisms for heating and/or cooling the gas inbladder 310. Further, to change the volume, balloon 300 may includepumps or other features for adding gas to and/or removing gas frombladder 310. Additionally or alternatively, to change the volume ofbladder 310, balloon 300 may include release valves or other featuresthat are controllable to allow gas to escape from bladder 310. Multiplebladders 310 could be implemented within the scope of this disclosure.For instance, multiple bladders could be used to improve balloonstability.

In an example embodiment, the envelope 302 could be filled with helium,hydrogen or other gaseous material with density less than typicalatmospheric gas (i.e., “lighter-than-air” gasses). The envelope 302could thus have an associated upward buoyancy force based on itsdisplacement. In such an embodiment, air in the bladder 310 could beconsidered a ballast tank that may have an associated downward ballastforce. In another example embodiment, the amount of air in the bladder310 could be changed by pumping air (e.g., with an air compressor) intoand out of the bladder 310. By adjusting the amount of air in thebladder 310, the ballast force may be controlled. In some embodiments,the ballast force may be used, in part, to counteract the buoyancy forceand/or to provide altitude stability.

In other embodiments, the envelope 302 could be substantially rigid andinclude an enclosed volume. Air could be evacuated from envelope 302while the enclosed volume is substantially maintained. In other words,at least a partial vacuum could be created and maintained within theenclosed volume. Thus, the envelope 302 and the enclosed volume couldbecome lighter than air and provide a buoyancy force. In yet otherembodiments, air or another material could be controllably introducedinto the partial vacuum of the enclosed volume in an effort to adjustthe overall buoyancy force and/or to provide altitude control.

In another embodiment, a portion of the envelope 302 could be a firstcolor (e.g., black) and/or formed of a first material different from therest of envelope 302, which may have a second color (e.g., white) and/ora second material. For instance, the first color and/or first materialcould be configured to absorb a relatively larger amount of solar energythan the second color and/or second material. Thus, rotating the balloonsuch that the first material is facing the sun may act to heat theenvelope 302 as well as the gas inside the envelope 302. In this way,the buoyancy force of the envelope 302 may increase. By rotating theballoon such that the second material is facing the sun, the temperatureof gas inside the envelope 302 may decrease. Accordingly, the buoyancyforce may decrease. In this manner, the buoyancy force of the ballooncould be adjusted by changing the temperature/volume of gas inside theenvelope 302 using solar energy. In such embodiments, it is possiblethat a bladder 310 may not be a necessary element of balloon 300. Thus,in various contemplated embodiments, altitude control of balloon 300could be achieved, at least in part, by adjusting the rotation of theballoon with respect to the sun to selectively heat/cool the gas withinthe envelope 302 and thereby adjust the density of such gas.

Further, a balloon 306 may include a navigation system (not shown). Thenavigation system may implement positioning functions to maintainposition within and/or move to a position in accordance with a desiredspatial distribution of balloons (balloon network topology). Inparticular, the navigation system may use altitudinal wind data todetermine altitudinal adjustments that result in the wind carrying theballoon in a desired direction and/or to a desired location. Thealtitude-control system may then make adjustments to the density of theballoon envelope 302 to effect the determined altitudinal adjustmentsand thereby cause the balloon 300 to move laterally to the desireddirection and/or to the desired location. Additionally or alternatively,desired altitudinal adjustments may be computed by a ground-based orsatellite-based control system and communicated to the balloon 300. Inother embodiments, specific balloons in a balloon network may beconfigured to compute altitudinal adjustments for other balloons andtransmit the adjustment commands to those other balloons.

Several example implementations are described herein. It will beunderstood that there are many ways to implement the devices, systems,and methods disclosed herein. Accordingly, the following examples arenot intended to limit the scope of the present disclosure.

3. Ground-Facing Antennas

FIG. 4A illustrates an example high-altitude balloon 402 with aground-facing antenna situated to illuminate a geographic region 406 atground level. The balloon 402 can be similar to the balloon 300described in connection with FIG. 3 and can include an RF communicationsystem mounted to a payload for operating the ground-facing antenna,similar to the RF communication system 318 in the payload 306 of theballoon 300. The ground-facing antenna emits radiation in an emissionpattern 404 that causes signals at ground level to substantially spanthe geographic region 406 while the balloon is at altitude A₁.Similarly, FIG. 4B illustrates the balloon 402 at altitude A₂ andilluminating the geographic region 406 by emitting radiation from theground-facing antenna with an emission pattern 405 so as tosubstantially span the geographic region 406 at ground level. Theemission pattern 404 used at altitude A₁ has a characteristic angularspan θ₁, while the emission pattern 405 used at altitude A₁ has acharacteristic angular span θ₂. While the antenna and its adjustableemission patterns 404, 405 are described herein in connection with thehigh-altitude balloon 402 for purposes of convenience, it isspecifically noted that such an antenna with adjustable emission patternmay be mounted to, and used in connection with, a variety of highaltitude platforms, such as other lighter-than-air devices and the like.

As illustrated in FIGS. 4A and 4B, the angular span θ₁ can be largerthan θ₂, such that the emission pattern 404 spans roughly the same areaat ground level (i.e., the area of geographic region 406) as the areaspanned by emission pattern 405, even while the first altitude A₁ islower than the second altitude A₂. The balloon's antenna can beconfigured such that the emission patterns 404, 405 (and respectiveangular spans θ₁, θ₂) at least approximately span the same ground levelgeographic region 406 regardless of the elevation of the balloon 402.Thus, the balloon 402 can be configured to maintain communication with asubstantially fixed geographic region (i.e., the region 406) even as theballoon ascends and descends to various elevations.

Moreover, the more directed emission pattern 405 shown in FIG. 4B, asindicated by the smaller angle θ₂, may have a greater directional gain.As such, the increased directional gain of emission pattern 405 may atleast partially compensate for the greater distance between the balloon402 and the ground level in FIG. 4B (i.e., the altitude A₂). Forexample, the radiation at ground level in the geographic region 406 mayhave comparable intensity whether from the more broadly emission pattern404 with the balloon 402 at altitude A₁ or from the more narrowly beamedemission patter 405 with the balloon 402 at altitude A₂. Generally, theintensity of radiation at ground level from emission pattern 405, withangular span θ₂, may be greater than radiation that would be providedfrom the same altitude by emission pattern 404, with angular span θ₁,and so the more directed emission pattern 405 thereby at least partiallycompensates for the altitude-dependent variations in radiation intensityat ground level.

In some examples, the first altitude A₁ may be near a low end of adesired stratospheric altitude for the high-altitude balloon 402 (e.g.,18 km), and the second altitude A₂ may be near a high end of a desiredstratospheric altitude for the high altitude balloon 402 (e.g., 25 km).The angular span θ₁ of the emission patterns 404 can be approximately90° (e.g., an approximately conical radiation pattern with a 45°half-width), and the angular span θ₂ of the emission pattern 405 can beapproximately 70° (e.g., an approximately conical radiation pattern witha 36° half-width).

In a further example, the emission pattern can be adjusted to accountfor variations in ground-level elevation. For example, the balloon 402can include an antenna with an emission pattern that is adjusted basedon the altitude of the balloon 402, relative to ground level immediatelybelow the balloon 402. In other words, the emission pattern can beadjusted based on the absolute altitude, relative to sea-level, such asdetected by ambient pressure, and can additionally or alternatively beadjusted based on altitude, relative to ground. Thus, the balloon 402may be configured to at least partially compensate for variations inrelative altitude (e.g., due to the balloon passing over regions withvariations in ground level altitude) in order to maintain an at leastapproximately constant geographic span and/or intensity level ofradiation reaching ground level. In one example, the balloon 402 maytraverse over a region with a series of ground elevation changes (e.g.,hills, valleys, slopes, flat areas, mountains, etc.). The balloon 402can dynamically adjust the radiation pattern of its ground-facingantenna to at least partially compensate for altitude-dependentvariations in the radiation that reaches the ground from the balloon402. For example, the emission pattern may be relatively broad, similarto the emission pattern 404 with angular span θ₁ shown in FIG. 4A, whileover a high elevation region, and thus relatively low relative altitude.Similarly, the emission pattern may be relatively narrow, similar to theemission pattern 405 with angular span θ₂ shown in FIG. 4B, while over alow elevation region, and thus relatively high relatively altitude.

In some examples, the relative altitude (i.e., distance from ground toballoon 402) can be determined by predetermined ground-level elevationdata in combination with position information (e.g., as determined by aGPS receiver or the like) and one or more altitude sensors on theballoon 402 (e.g., altimeters and/or pressure sensors and the like).Upon determining position information for the balloon, such as latitudeand longitude coordinates, a mapping database can be accessed todetermine a corresponding ground level elevation immediately below theballoon 402. The ground-level elevation, which can be determined by acomputer system on the balloon 402 (e.g., similar to the computer system312 in the payload 306 of the balloon 300) and/or by a remote server incommunication with the balloon 402, can then be combined with thealtitude of the balloon 402 as determined via the on-board sensors todetermine the distance from the balloon 402 to the ground (i.e., therelative altitude). In other examples, the balloon 402 may includesensors configured to directly sense and/or determine the relativealtitude of the balloon 402, such as downward facing radar and the like.

In a further example, the emission pattern can be adjusted to accountfor influences on the radiation from the balloon due to atmosphericeffects, such as weather patterns in the troposphere. As an example,particular portions of the spectrum may be sensitive to inclementweather due to increases in radiation attenuating water vapor and/ordroplets in the troposphere, for example. To achieve a desired radiationintensity at ground level (e.g., a minimum signal to noise ratio), theemission pattern may be narrowed in response to detecting certainweather patterns. In other words, the radiation pattern may be narrowedso as to increase the directional gain in the illuminated region atground level, to account for radiation attenuating weather patterns inthe atmosphere between ground level and the high-altitude balloon 402.In some examples, such weather-related effects can be accounted for bysystems that dynamically detect weather patterns and communicateaccordingly with the balloon 402. In other examples, suchweather-related effects can be detected directly via sensors on theballoon 402. Additionally or alternatively, such weather conditions(and/or other signal degrading phenomena) can be inferred throughdetection of degradation in signal strength at stations at ground-level.In other words, the signal to noise ratio (or other measure of signalstrength) at ground-based stations can be used as feedback informationto dynamically adjust the emission pattern, and thus the direction gain,of the ground-facing antenna on the balloon 402.

Some embodiments of the present disclosure accordingly provide forground-facing antennas with emission pattern that change based onaltitude. The ground-facing antennas can change emission pattern in amanner that at least partially compensates for variations in theradiation at ground level that would otherwise occur due to altitudechanges. Such altitude-based compensations in emission pattern can beperformed by adjusting the distance between a radiating element and areflector in the ground-facing antenna. Examples of antennas withadjustable separation distances between radiator and reflectors aredescribed next.

As a preliminary matter, it is noted that the discussion hereingenerally refers to transmission of radio signals according toadjustable emission patterns (or radiation patterns) to illuminategeographic regions (e.g., the geographic region 406 at ground levelilluminated by the emission patterns 404, 405). However, due to thegeneral reciprocity between emission and reception of radio signals inantenna theory and design, it is recognized that the discussionthroughout generally has equal application to the reception of signalsfrom a particular ground-level geographic region. That is, the antennaswith altitude-dependent adjustable radiation patterns may be usedadditionally or alternatively to receive signals arriving from theradiation patterns (e.g., from within the geographic region 406 atground level). In such an example, adjusting the radiation patternallows the receiving antenna (mounted to the high-altitude balloon) toat least partially compensate for the change in sensitivity thatnaturally accompanies changes in altitude. For example, such antennasmay increase their directional gain at higher altitudes, as shown inFIGS. 4A and 4B.

FIG. 4C illustrates a ground-facing antenna 408 with a radiator 420, areflector 410, and a linkage 440 that controls the separation distanced₁ between the radiator 420 and reflector 410 to provide an emissionpattern with angular span θ₁. FIG. 4D illustrates the ground-facingantenna 408 of FIG. 4C, but with a greater separation distance d₂between the radiator 420 and reflector 410, which results in a moredirected emission pattern, as indicated by the angular span θ₂. Theground-facing antenna 408 shown in FIGS. 4C and 4D can be mounted to apayload of a high-altitude balloon to radiate downward while the balloonis aloft, similar to the balloon 402 described in connection with FIGS.4A and 4B with a payload-mounted ground-facing antenna. In an examplewhere the antenna 408 is mounted to the payload of the balloon 402, theconfiguration of the antenna 408 in FIG. 4C, with separation distance d₁and emission pattern angular span θ₁, can be used to provide theemission pattern 404 with the balloon at altitude A₁ (FIG. 4A).Similarly, the configuration of the antenna 408 in FIG. 4D, withseparation distance d₂ and emission pattern angular span θ₂, can be usedto provide the emission pattern 405 with the balloon at altitude A₂(FIG. 4B).

As shown in FIG. 4C, a transmitter 430 is connected to the radiator 420via a transmission line 432. The transmitter 430 can be included in, orin communication with, a computer system and/or RF communication systemwithin the payload of a balloon to which the antenna 408 is mounted,similar to the computer system 312 and RF communication system 318described in connection with the balloon 300 in FIG. 3. The transmitter430 can thus provide input signals to the radiator 420 to cause theradiator 420 to emit corresponding radiation 422, 424, which radiationis then reflected by the reflector 410. Although it is noted that insome embodiments in which the antenna 408 is used to receive incomingradiation, the transmitter 430 may be replaced by a receiver configuredto receive information based on harvested radio energy radiating throughfree space to excite the antenna element 420.

The radiator 420 can be any type of directional or non-directionalradiating element suitable for emitting signals according to inputs,such as a horn feed antenna, a bi-pole antenna, etc. The reflector 410can be a solid or non-solid (e.g., mesh), and may be sphericallyinvariant dish (e.g., the reflective surface of the dish may beequidistant from a common point, or spherical center). In some examples,the reflector 410 may be a cylindrically symmetric dish with a concavecurvature defined by a parabolic curvature. In some examples, moreover,the reflector 410 may be a single flat, planar reflective surface, ormay be formed of multiple flat panels which may be co-planar or may becombined to create a general concave or convex curvature so as to directthe radiation 422, 424 emitted from the radiator 420 according to adesired pattern.

As shown in FIG. 4C, the radiator 420 is separated from the reflector410 by a distance d₁. The transmitter 430 provides input signals to theradiator 420 to cause the radiator 420 to emit radiation 422 toward thereflector 410. The radiation 422 from the radiator 420 is then reflectedby the reflector 410 and directed in an emission pattern with angularspan θ₁ (e.g., a conical radiation pattern with apex approximatelylocated at the antenna 408 and opening angle θ₁). The angular span ofthe resulting emission pattern is determined, at least in part, by theseparation distance between the radiator 420 and the reflector 410.Assuming symmetric reflections about incident angles for radiationreflected from the reflector 410, ray tracing radiation from theradiator 420 to the reflector 410 and then outward away from thereflector 410 shows that the angular span of radiation reflected fromthe reflector 410 is increased at lower separation distances d₁, andvice versa. Thus, the configuration of the antenna 408 in FIG. 4D, withseparation distance d₂>d₁ by difference Δd results in an emissionpattern with a decreased angular span θ₂.

A linkage 440 controls the separation distance between the radiator 420and the reflector 410. The linkage 440 may be a structure that isconnected to one or both of the radiator 420 or the reflector 410 andincludes adjustable elements, telescoping components, pulleys, wheels,gears, stepper motors, etc., to cause the radiator 410 to move withrespect to the reflector 420 or vice versa, and thereby control theseparation distance between the two. The linkage 440 may include one ormore support arms that connect to the radiator 410 to suspend theradiator 410 above the reflector 420. In some examples, the reflector410 may be mounted to a fixed portion of the balloon's payload, whilethe radiator 410 is able to move toward and away from the reflector 420via the linkage 440. In other examples, the radiator 410 may be mountedto a fixed portion of the balloon's payload, while the reflector 420 isable to move toward and away from the radiator 410 via the linkage 440.Other examples are also possible to allow the linkage 440 to adjust theseparation distance between the radiator 410 and the reflector 420.Thus, FIG. 4D may illustrate the linkage 430 in an extended state inwhich the separation distance d₂ is increased by difference Δd, relativeto a compressed state illustrated in FIG. 4C in which the linkage 430provides a separation distance d₁.

The configuration of the radiator 410 and reflector 420 in FIGS. 4C and4D are provided for purposes of illustration and example only, and notlimitation. In other examples, alternative arrangements may be used,such as arrangements with multiple reflection points (e.g., antennadesigns incorporating sub-reflectors), and combinations of convex,concave, and/or flat reflectors to provide variable focal lengths andthus variable radiation patterns.

3a) Altitude-Adjustable Linkages

FIG. 5A is a simplified block diagram of an antenna 500 with adynamically adjustable emission pattern. The antenna 500 is configuredto mounted to a payload of a high-altitude balloon (or another highaltitude platform) in a ground-facing orientation, similar to theantenna described in connection with FIGS. 4A-4D. The antenna 500includes a radiator 520, a reflector 510, and a linkage 540 thatcontrols the separation distance d_(SEP) between the radiator 520 andthe reflector 510. The linkage 540 is configured to adjust theseparation distance d_(SEP) according to instructions from a controller550.

The controller 550 can include a combination of hardware and/or softwareimplemented modules included in the payload of the balloon to which theantenna 500 is mounted. The controller 550 can be configured todetermine the altitude of the antenna 500, such as via altitudedetermination logic 552, which may include computer-readableinstructions for being executed by a processor. The controller 550 maythus include (or be included in) a computer system similar to thecomputer system 312 in the payload 306 of the balloon 300 described inconnection with FIG. 3. To determine the altitude of the antenna 500,the controller 550 receives sensor inputs 554. The sensor inputs 554 caninclude information from pressure and/or temperature sensors (e.g., analtimeter). The sensor inputs 554 can also include information fromgeo-location navigation and/or communication systems, such as positioninformation derived from time-of-flight measurements to/from referenceobjects, (e.g., GPS satellites, other high-altitude balloons,ground-based stations, etc.).

In operation, the sensor inputs 554 provide inputs to the controller550, which inputs are indicative of the altitude of the balloon to whichthe antenna 500 is mounted. The controller 550 analyzes the informationfrom the sensor inputs 554 to determine the altitude of the balloon(e.g., via the altitude determination logic 552). For example,measurements of pressure and/or temperature, and/or time-of-flightdelays to reference objects can be analyzed by the controller 550 (viathe altitude determination logic 552) to determine the altitude of theballoon. The controller 550 can then instruct the linkage 540 to adjustthe separation distance d_(SEP) between the radiator 520 and thereflector 510, which adjustment results in a change in the emissionpattern of the antenna 500. In some examples, the controller 550operates to provide instructions to the linkage 540 that cause theseparation distance d_(SEP) to increase in response to a decreasedaltitude (as determined by the altitude determining logic 552).Additionally, the controller 550 can provide instructions to cause theseparation distance d_(SEP) to decrease in response to an increasedaltitude (as determined by the altitude determining logic 552).

Moreover, the controller 550 can be configured to additionally oralternatively detect other inputs and cause the separation distanced_(SEP) to be adjusted accordingly. For example, the controller 550 caninstruct the linkage 540 to adjust the separation distance based onvariations in relative altitude (e.g., distance from ground level to theantenna), variations in weather conditions (e.g., estimates oftropospheric water vapor and/or water droplet density), and/or othervariations in received signal conditions at ground-level signal (e.g.,as indicated by feedback on received signal strength at groundstations), as described in connection with FIGS. 4A and 4B above.

The linkage 540 can include one or more components configured to adjustmechanical length in response to suitable instructions from thecontroller 550. For example, the linkage 540 may include telescopingcomponents, elastic components, other moveable components, etc., andassociated motors, gears, pulleys, etc., configured to modify therelative position(s) of such moveable components according to theinstructions from the controller 550. Moreover, the linkage 540 mayinclude one or more devices configured to provide position feedbackinformation on the state of the linkage 540 (e.g., the relativepositions of the various moveable components). The feedback devices canbe, for example one or more encoders and/or other position sensor(s).Such feedback devices can then provide feedback position data to thecontroller 550, which can use the data to estimate the present value ofd_(SEP), and then further refine instructions to the linkage on whetherand how to adjust the linkage 540. Thus, the instructions to the linkage540 from the controller 550 may be based on one or both oflinkage-position feedback data or altitude-indicative sensor data (554).

FIG. 5B is a simplified block diagram of another antenna 501 with adynamically adjustable emission pattern. Whereas the antenna 500described in connection with FIG. 5A actively determines the altitude ofthe antenna, and then causes the separation distance d_(SEP) to adjust(e.g., by sending suitable electronic signals), the antenna 501 isconfigured to passively adjust the separation distance d_(SEP) betweenthe radiator 520 and the reflector 510 in response to changes inatmospheric pressure.

In the antenna 501, the radiator 520 is mounted to a supportingstructure 545, which may be one or more support arms that suspend theradiator 520 below the reflector 510. For example, the supportingstructure 545 may be an arrangement of support arms situated in a planeapproximately parallel to the reflector 510. The supporting structure545 can then be connected to anchor points 560 a-b via respectivepressure-sensitive vessels 540 a-b. The anchor points 560 a-b can bestructural points connected to the payload of the balloon to which theantenna 501 is mounted, and such anchor points can be substantiallyfixed in position with respect to the reflector 510, which is alsomounted to the payload of the balloon.

The pressure-sensitive vessels 540 a-b can be containers with flexiblesidewalls that allow the vessels 540 a-b to expand and contract alongtheir length. For example, the vessels 540 a-b can have end caps eachextending perpendicular to their respective lengths, which join to theflexible sidewalls. In FIG. 5B, the supporting structure 545 and anchorpoints 560 a-b can be connected to opposing end caps of the vessels 540a-b, such that the flexible sidewalls extend between the two. Byorienting the vessels 540 a-b with adjustable lengths between thesupporting structure 545 and the anchor points 560 a-b, adjusting thelength of the pressure-sensitive vessels 540 a-b causes a correspondingadjustment in the separation distance d_(SEP) between the radiator 520and the reflector 510.

The pressure-sensitive vessels 540 a-b adjust their lengths in responseto changes in external pressure (i.e., atmospheric pressure). Thepressure-sensitive vessels 540 a-b may include an internal chamber thatis substantially evacuated (e.g., near vacuum pressure). As such, theflexible side walls can have sufficient structural rigidity to preventthe vessel from collapsing on itself, even when the chamber issubstantially evacuated. The flexible side walls may be formed, forexample, of corrugated metal that resists compression, but deforms(e.g., bends) to allow the vessel to contract in length. The amount ofcompression (and thus mechanical deformation) can thus depend on theamount of external force urging the vessel to a decreased volume, whichforce can be supplied by ambient pressure. For the vessels 540 a-b,which are substantially flexible only along their length, theexpansion/contraction in volume is an expansion/contraction in length,and therefore separation distance d_(SEP) between the radiator 520 andthe reflector 510. In some examples, another semi-rigid material may beemployed additionally or alternatively to corrugated metal to allow thevessel to contract systematically in response to changes in ambientpressure.

By using a pressure-sensitive vessel that is substantially evacuated(e.g., by providing pressure near vacuum in the internal chamber), thevessels 540 a-b desirably exhibit greater insensitivity to temperaturevariations than comparable vessels filled with fluid, such as gas. Forexample, at high altitudes, a high altitude platform may alternatebetween receiving large exposures of solar radiation and receivingvirtually no radiation, depending on night time or day time. Duringperiods in which the high altitude platform is exposed to the solarradiation (e.g., during daytime hours for a geostationary platform), anygas trapped within the pressure-sensitive vessel would be heated, andundergo expansion. Similarly, during periods lacking exposure to solarradiation (e.g., during nighttime hours for a geostationary platform),such gas would be cooled, and undergo contraction. Suchtemperature-dependent expansion and contraction of gas within thepressure-sensitive vessels would be substantially independent ofvariations in altitude and may therefore have to be separatelycompensated for. Other sources of thermal variations are also possible,such as due to operation of electronics on the payload of the highaltitude platform, and other sources. However, evacuating the internalchambers of the pressure-sensitive vessels substantially eliminatestemperature-dependent pressure fluctuations of the internal chamber ofsuch vessels.

Alternatively, the internal chamber may be filled with a fluid, such asa gas, and the internal chamber may be in fluid connection with at leastone of the end caps of the vessel 540 a, such that the pressure withinthe internal chamber at least approximately balances the externalpressure on the pressure-sensitive vessel 540 a. The internal chambermay be sealed, such that the pressure within the internal chamber isinversely proportionate to the volume of the vessel 540 a. Thus, at lowambient pressure, the pressure-sensitive vessel expands to a largevolume to allow the pressure in the internal chamber to at leastapproximately balance the atmospheric pressure. Similarly, at highambient pressure, the pressure-sensitive vessel contracts to a smallervolume. As noted above, gas within the vessels 540 a-b, can cause thevessels to expand and contract with dependence on temperature variationsseparate from altitude-dependent temperature variations, so theseparation distance d_(SEP) may then have a separate temperature-basedcompensation system.

The antenna 501 passively adjusts d_(SEP) based on altitude, because thepressure of the stratosphere generally decreases with altitude, andtherefore serves as a proxy for altitude sensitivity. As a result, theantenna 501 has a greater separation distance (and therefore narrowerradiation pattern) at greater altitudes where the ambient pressure islower and the pressure-sensitive vessels 540 a-b therefore expand.Similarly, the antenna 501 has a lesser separation distance (andtherefore broader radiation pattern) at lesser altitudes where theambient pressure is greater and the pressure-sensitive vessels 540 a-btherefore contract.

FIG. 5C is a simplified block diagram of another antenna 502 with adynamically adjustable emission pattern. The antenna 502 is similar tothe antenna 501, except that the radiator 520 is disposed so as to besubstantially fixed with respect to the payload of the balloon to whichthe antenna 502 is mounted, and the reflector 510 is suspended to movewith respect to the radiator 520. The reflector 510 can be connected toa supporting structure 546, which supporting structure is then connectedto one or more anchor points 562 a-b via pressure-sensitive vessels 542a-b. The anchor points 562 a-b can be substantially fixed with respectto the payload of the balloon to which the antenna 502 is mounted (andalso with respect to the radiator 520). The separation distance d_(SEP)between the radiator 520 and the reflector 510 is thus automaticallyadjusted in response to changes in ambient pressure due toexpansion/contraction of the pressure-sensitive vessels 542 a-b, whichexpansion/contraction moves the supporting structure 546, and thus thereflector 510, with respect to the anchor points 562 a-b. As compared tothe antenna 501 in FIG. 5B, the configuration of the antenna 502 shownin FIG. 5C may allow for the radiator 520 to be fixed structurally withrespect to the payload of the balloon. As a result, the transmissionline for signals feeding the radiator 520 can be connected along afixed, non-moveable structural element.

In some examples, the pressure-sensitive vessel(s) 540 a-b, 542 a-b caneach be a generally cylindrical container with corrugated (e.g., ribbed)metallic sidewalls, similar to a bellows or an aneroid employed inbarometric sensors. While FIGS. 5B and 5C illustrate multiplepressure-sensitive vessels connected to the radiator 520 (via thesupporting structure 545) and/or the reflector 520 (via the supportingstructure 546), some embodiments of adjustable linkages may include justone pressure-sensitive vessel or more than two pressure-sensitivevessels.

Examples of pressure-sensitive vessels configured as aneroids (e.g.,vessels with at least one flexible surface capable of contraction orexpansion in response to are described below in connection with FIG. 6.However, some examples may additionally or alternatively include ahollow tube that is arranged to coil/uncoil in response to ambientpressure changes (e.g., a Bourdon tube, etc.) and/or other systems ordevices that mechanically respond to variations in ambient pressure. Anantenna may be configured to modify its beaming pattern based on themechanical response of such systems or devices.

Moreover, while some embodiments of the present disclosure may apply toantennas with at least one radiator and at least one reflector, someembodiments may apply to antennas with a variety of other form factors.For example, some embodiments may apply to antennas with multipleradiators (e.g., driven elements) and/or multiple reflectors (e.g.,passive elements). In some embodiments a Yagi-type antenna (and/or otherantennas including dipole elements and/or parasitic elements) may beconfigured such that one or more driven elements and/or one or morepassive elements (e.g., directors, reflectors, etc.) have spatialseparations that depend, at least in part, on a pressure-sensitivevessel (and/or other systems or devices that mechanically respond tovariations in ambient pressure). The pressure-dependent relative spacingbetween the driven elements and/or passive elements may then cause thedirectivity (e.g., beaming pattern) of such an antenna to be modifiedbased on antenna altitude. Thus, in some examples, a Yagi type antenna(or another antenna with multiple driven elements and/or passiveelements) can have relative spacing between elements adjusted in analtitude-dependent manner such that the resulting radiation pattern isadjusted in an altitude-dependent manner (e.g., so as to at leastpartially compensate for ground level variations in geographicalboundaries and/or intensity of the radiation pattern).

3b) Pressure-Sensitive Vessel

FIG. 6A shows a pressure-sensitive vessel 600 in an expanded state. FIG.6B shows the pressure-sensitive vessel 600 in a contracted state. Thepressure-sensitive vessel 600 includes a first end cap 602 and a secondend cap 604. A flexible sidewall 610 connects the first and second endcaps 602, 604 so as to enclose an inner chamber. The inner chamber canbe substantially evacuated, and can have a pressure near vacuum. Theflexible sidewall 610 includes a plurality of alternating ridges 614 a-cand grooves 612 a-b along a direction transverse to the length of thevessel 600, which extends between the two end caps 602, 604. Thealternating ridges 614 a-c and grooves 612 a-b combine to create acorrugated structure that allows the flexible sidewall 610 toexpand/contract along the length of the vessel 600. The flexiblesidewall 610 and/or the end caps 602, 604 can be formed of a rigidmetallic material, such as aluminum, for example. In addition, jointsand/or seams in the pressure-sensitive vessel can be sealed withflexible sealants and/or films, such as polymeric materials and the likein order to seal the inner chamber enclosed by the end caps 602, 604 andthe flexible sidewall 610.

For example, the vessel 600 can expand/contract by flexing the jointsalong the corrugated ridges 614 a-c and grooves 612 a-b of the flexiblesidewall 610. In the expanded state, shown in FIG. 6B, the length of thepressure-sensitive vessel 600 (e.g., the distance between the opposingend caps 602, 604) is L_(EXP). In FIG. 6B, in the contracted state, thelength of the pressure-sensitive vessel 600 is L_(COMP). By forming thepressure-sensitive vessel 600 of rigid materials configured toexpand/contract in one dimension (via the flexible sidewall 610), thepressure-sensitive vessel 600 harnesses pressure-sensitiveexpansion/contraction of the volume of the vessel 600 to cause thevessel 600 to change length.

In FIG. 6A, the pressure-sensitive vessel 600 can be in a low ambientpressure environment, such as encountered at high altitudes in thestratosphere (e.g., approximately 25 km). The low ambient pressurecreates relatively little force on the external walls of thepressure-sensitive vessel 600 and the flexible sidewall 610 expands tocause the vessel 600 to have length L_(EXP). In FIG. 6B, thepressure-sensitive vessel 600 can be in a higher ambient pressureenvironment, such as encountered at low altitudes in the stratosphere(e.g., approximately 18 km). The higher ambient pressure creates arelatively greater force on the external walls of the pressure-sensitivevessel 600 and the flexible sidewall 610 contracts to cause the vessel600 to have length L_(COMP).

Generally, the pressure-sensitive vessel 600 can include an internalchamber that is at a low pressure so that gas remaining in the chamberexerts less pressure than the atmosphere on the sidewalls. For example,the internal chamber can be at a vacuum or near vacuum pressure. Inoperation, when air pressure outside the chamber increases or decreases,the flexible sidewall 610 allows the aneroid (or other vessel) tocontract or expand, respectively. In some embodiments, the flexiblesidewall 610 acts as a spring to prevent the aneroid from collapsing. Assuch, suitable materials for this flexible surface include aluminum,stainless steel, brass, copper, Monel, and/or bronze. Other metals orplastics that maintain their spring rate with varied temperatures andmultiple expansion and contraction cycles are also contemplated herein.In some embodiments, the aneroid may take the form of: a chamber with abottom surface, a top surface and at least one collapsible sidewall orother flexible surface, a bellows, a capsule with a flexible diaphragm,and/or a stacked pile of pressure capsules with corrugated diaphragms.The foregoing list is not intended to be exhaustive and is providedmerely by way of example.

3c) Flat Reflector Antennas

FIG. 7A is a simplified diagram of an antenna 700 with a flat reflector708. The antenna 700 shown in FIG. 7A can be configured to be mounted toa payload of a high-altitude balloon so as to be ground-facing, similarto the antennas described above in connection with FIG. 4-5. A radiatingelement 702 is situated under the flat reflector 708, and radiatesaccording to input signals (e.g., from a transmitter). The radiatingelement 702 and reflector 708 can be similar to a patch antenna in someexamples. In some examples, the radiating element can be a planarconductive component. The radiating element may be approximately 50millimeters by 50 millimeters or may have other dimensions, includingnon-square dimensions (e.g., rectangular, etc.). The reflector 708 canbe a planar conductive component plane parallel to the radiating element702. The reflector may be approximately 300 millimeters by 300millimeters or may have other dimensions, including non-squaredimensions (e.g., rectangular, etc.). A support arm 704 suspends theradiating element 702 with respect to the reflector 708, and can also beused to convey transmission signals to the radiating element 702. Asshown in FIG. 7A, the radiating element 702 and/or reflector 708 may berectangular in shape, and may even be square, for example.

An adjustable linkage 706 connects to the supporting arm and isconfigured to adjust the separation distance d_(SEP) between theradiating element 702 and the reflector 708 according to the altitude ofthe antenna 700. The linkage 706 may be an active linkage with moveablecomponents that are operated to adjust the separation distance based ona determined altitude of the antenna, similar to the active adjustablelinkages described in connection with FIG. 5A. Additionally oralternatively, the linkage 706 may be a passive linkage that includesone or more pressure-sensitive vessels connected so as to adjust theseparation distance d_(SEP) in response to changes in ambient pressure,similar to the passive adjustable linkages described in connection withFIGS. 5B and 5C.

FIG. 7B is a simplified diagram of another antenna 710 with a flatreflector 718. The antenna 710 shown in FIG. 7B can be configured to bemounted to a payload of a high-altitude balloon so as to beground-facing, similar to the antennas described above in connectionwith FIG. 4-5. A radiating element 712 is situated under the flatreflector 718, and radiates according to input signals (e.g., from atransmitter). The radiating element 712 and reflector 718 can be similarto a patch antenna in some examples. In some examples, the radiatingelement can be a planar conductive component with an approximate area of50 millimeters squared. The reflector 718 can be a planar conductivecomponent plane parallel to the radiating element 712 and with anapproximate area of 300 millimeters squared. A support arm 714 suspendsthe radiating element 712 with respect to the reflector 718, and canalso be used to convey transmission signals to the radiating element712. As shown in FIG. 7B, the radiating element 712 and/or reflector 718may have rounded edges, and may even be circular, for example.

An adjustable linkage 716 connects to the supporting arm and isconfigured to adjust the separation distance d_(SEP) between theradiating element 712 and the reflector 718 according to the altitude ofthe antenna 710. The linkage 716 may be an active linkage with moveablecomponents that are operated to adjust the separation distance based ona determined altitude of the antenna, similar to the active adjustablelinkages described in connection with FIG. 5A. Additionally oralternatively, the linkage 716 may be a passive linkage that includesone or more pressure-sensitive vessels connected so as to adjust theseparation distance d_(SEP) in response to changes in ambient pressure,similar to the passive adjustable linkages described in connection withFIGS. 5B and 5C

4. Example Methods

FIG. 8A is a flowchart of a process 800 for dynamically adjusting anantenna emission pattern according to an example embodiment. The process800 illustrated in FIG. 8A may be implemented by any of theground-facing balloon-mounted antennas described herein alone or incombination with hardware and/or software implemented functionalmodules. At block 802, radiation is emitted from a ground-facing antennamounted to a high-altitude balloon. For example, radiation may beemitted from the antenna 408 so as to illuminate a geographic region atground level, as described in connection with FIG. 4. At block 804, theemission pattern of the antenna is adjusted in response to a change inaltitude of the antenna. For example, as described in connection withFIG. 4, the emission pattern of antenna 408 can change from a broadpattern with angular span θ₁ while at altitude A₁ to a more directedpattern with angular span θ₂ upon reaching altitude A₂. At block 806,the antenna emits radiation according to the adjusted emission patternwhile at the new altitude. As indicated by the dashed arrow, the process800 can optionally be repeated to cause the emission pattern to beintermittently (or perhaps even continuously) updated according to thethen present altitude of the antenna.

Moreover, at block 804, the emission pattern can additionally oralternatively be adjusted in response to a change in other aspectsinfluencing signal propagation between ground level and an antenna athigh altitude. For example, the emission pattern can be adjusted basedon variations in relative altitude (e.g., distance from ground level tothe antenna), variations in weather conditions (e.g., estimates oftropospheric water vapor and/or water droplet density), and/or othervariations in received signal conditions at ground-level signal (e.g.,as indicated by feedback on received signal strength at groundstations), as described in connection with FIGS. 4A and 4B above.

FIG. 8B is a flowchart of a process 810 for dynamically adjusting anantenna emission pattern according to an example embodiment. The process810 illustrated in FIG. 8B may be implemented by any of theground-facing balloon-mounted antennas described herein alone or incombination with hardware and/or software implemented functionalmodules. At block 812, radiation is emitted from a ground-facing antennamounted to a high-altitude balloon. For example, radiation may beemitted from the antenna 408 so as to illuminate a geographic region atground level, as described in connection with FIG. 4. At block 814, theantenna components and/or associated control systems determine whetherthe antenna have increased in altitude. If the altitude is increased,the emission pattern of the antenna is adjusted by increasing theseparation distance between the reflector and the radiator of theantenna (816). The increased separation distance causes the resultingradiation pattern of the antenna to have a narrower angular span (e.g.,to be more directed, similar to the emission pattern 405 with angularspan θ₂ in FIG. 4B). The process 810 then returns to block 812 to emitradiation from the ground-facing antenna.

Block 814 may involve altitude determining logic receiving sensor inputsand determining altitude of the antenna, similar to the discussion ofthe altitude determining logic 552 in FIG. 5A. However, the decision inblock 814 may also be implicitly performed by a passive,pressure-sensitive vessel, similar to the passive altitude-sensitivelinkages described in connection with FIGS. 5B and 5C that adjust theseparation distances between radiator and reflector based on ambientpressure, which is a proxy for altitude.

If block 814 determines no increase in altitude, at block 818, theantenna components and/or associated control systems determine whetherthe antenna have decreased in altitude. If the altitude is decreased,the emission pattern of the antenna is adjusted by decreasing theseparation distance between the reflector and the radiator of theantenna (820). The decreased separation distance causes the resultingradiation pattern of the antenna to have a broader angular span (e.g.,to be more dispersed, similar to the emission pattern 404 with angularspan θ₁ in FIG. 4A). The process 810 then returns to block 812 to emitradiation from the ground-facing antenna.

Similar to block 814, block 818 may involve altitude determining logicreceiving sensor inputs and determining altitude of the antenna, similarto the discussion of the altitude determining logic 552 in FIG. 5A.However, the decision in block 818 may also be implicitly performed by apassive, pressure-sensitive vessel, similar to the passivealtitude-sensitive linkages described in connection with FIGS. 5B and 5Cthat adjust the separation distances between radiator and reflectorbased on ambient pressure, which is a proxy for altitude.

As indicated by the dashed arrow, the process 810 can optionally berepeated to cause the emission pattern to be intermittently (or perhapseven continuously) updated according to the then present altitude of theantenna.

In some embodiments, the disclosed methods may be implemented ascomputer program instructions encoded on a non-transitorycomputer-readable storage media in a machine-readable format, or onother non-transitory media or articles of manufacture. FIG. 9 is aschematic illustrating a conceptual partial view of an example computerprogram product that includes a computer program for executing acomputer process on a computing device, arranged according to at leastsome embodiments presented herein.

In one embodiment, the example computer program product 900 is providedusing a signal bearing medium 902. The signal bearing medium 902 mayinclude one or more programming instructions 904 that, when executed byone or more processors may provide functionality or portions of thefunctionality described above with respect to FIGS. 1-8. In someexamples, the signal bearing medium 902 may encompass acomputer-readable medium 906, such as, but not limited to, a hard diskdrive, a Compact Disc (CD), a Digital Video Disk (DVD), a digital tape,memory, etc. In some implementations, the signal bearing medium 902 mayencompass a computer recordable medium 708, such as, but not limited to,memory, read/write (R/W) CDs, R/W DVDs, etc. In some implementations,the signal bearing medium 902 may encompass a communications medium 910,such as, but not limited to, a digital and/or an analog communicationmedium (e.g., a fiber optic cable, a waveguide, a wired communicationslink, a wireless communication link, etc.). Thus, for example, thesignal bearing medium 902 may be conveyed by a wireless form of thecommunications medium 910.

The one or more programming instructions 904 may be, for example,computer executable and/or logic implemented instructions. In someexamples, a computing device such as the computer system 312 of FIG. 3may be configured to provide various operations, functions, or actionsin response to the programming instructions 904 conveyed to the computersystem 312 by one or more of the computer readable medium 906, thecomputer recordable medium 908, and/or the communications medium 910.

The non-transitory computer readable medium could also be distributedamong multiple data storage elements, which could be remotely locatedfrom each other. The computing device that executes some or all of thestored instructions could be a device, such as the balloon 300 shown anddescribed in reference to FIG. 3. Alternatively, the computing devicethat executes some or all of the stored instructions could be anothercomputing device, such as a server.

The above detailed description describes various features and functionsof the disclosed systems, devices, and methods with reference to theaccompanying figures. While various aspects and embodiments have beendisclosed herein, other aspects and embodiments will be apparent tothose skilled in the art. The various aspects and embodiments disclosedherein are for purposes of illustration and are not intended to belimiting, with the true scope being indicated by the following claims.

What is claimed is:
 1. An antenna configured to be mounted to an aerialvehicle, the antenna comprising: a radiator configured to emit radiationaccording to a feed signal; a reflector configured to direct radiationemitted from the radiator such that reflected radiation is characterizedby an emission pattern determined at least in part by a separationdistance between the radiator and the reflector, wherein the reflectoris configured to be situated such that the emission pattern is directedin a ground-facing direction while the aerial vehicle is aloft; and alinkage configured to adjust the separation distance between theradiator and the reflector according to an altitude of the aerialvehicle.
 2. The antenna according to claim 1, wherein the linkageincludes a vessel arranged such that a change in volume of the vesselcauses a corresponding change in the separation distance between theradiator and the reflector.
 3. The antenna according to claim 2, whereinthe vessel is configured such that the volume of the vessel is based onambient pressure, thereby causing the separation distance to be based atleast in part on the ambient pressure.
 4. The antenna according to claim2, wherein the vessel includes end caps connected between one or moresidewalls having a plurality of ribs to allow the vessel to changevolume, in response to changes in ambient pressure, substantially byexpanding or contracting a length of the one or more sidewalls, via theplurality of ribs, thereby changing a distance between the end caps, andwherein the end caps are connected such that the separation distancebetween the radiator and the reflector corresponds to the distancebetween the end caps.
 5. The antenna according to claim 4, wherein thevessel includes a generally cylindrically-shaped aneroid with at leastpartially corrugated metallic sidewalls, and wherein an internal chamberof the vessel is substantially evacuated.
 6. The antenna according toclaim 1, further comprising a controller configured to: (i) determinethe altitude of the aerial vehicle, and (ii) cause the linkage to adjustthe separation distance between the radiator and the reflector based onthe determined altitude.
 7. The antenna according to claim 1, whereinthe linkage is further configured to dynamically adjust the separationdistance between the radiator and the reflector by: (i) reducing theseparation distance responsive to an increase in altitude of theantenna, and (ii) increasing the separation distance responsive to adecrease in altitude of the antenna.
 8. The antenna according to claim1, wherein the separation distance is dynamically adjusted such that, ina geographical region receiving the emitted radiation at ground level,variations in intensity of the received radiation at ground level due tovariations in altitude of the aerial vehicle are at least partiallycompensated for.
 9. The antenna according to claim 1, wherein theseparation distance is dynamically adjusted such that, in a geographicalregion receiving the emitted radiation at ground level, variations in aboundary of the geographical region receiving the radiation due tovariations in altitude of the aerial vehicle are at least partiallycompensated for.
 10. The antenna according to claim 1, wherein theantenna is further configured to receive radiation from a region definedby the emission pattern.
 11. The antenna according to claim 1, whereinthe antenna is further configured to transmit signals to radio stationsat ground level.
 12. An aerial vehicle comprising: an envelope; apayload configured to be suspended from the envelope; and an antennamounted to the payload and situated so as to be ground-facing while theaerial vehicle is aloft, the antenna including: (i) a radiatorconfigured to emit radiation according to feed signals; (ii) a reflectorconfigured to direct the radiation emitted from the radiator accordingto a radiation pattern determined at least in part according to aseparation distance between the radiator and the reflector; and (iii) alinkage configured to adjust the separation distance between theradiator and the reflector according to an altitude of the aerialvehicle.
 13. The aerial vehicle according to claim 12, wherein thelinkage includes a vessel arranged such that a change in volume of thevessel causes a corresponding change in the separation distance betweenthe radiator and the reflector.
 14. The aerial vehicle according toclaim 13, wherein the vessel is configured such that the volume of thevessel is based on ambient pressure, thereby causing the separationdistance to be based, at least in part, on the ambient pressure.
 15. Theaerial vehicle according to claim 13, wherein the vessel includes endcaps connected between one or more sidewalls having a plurality of ribsto allow the vessel to change volume, in response to changes in ambientpressure, substantially by expanding or contracting a length of the oneor more sidewalls, via the plurality of ribs, thereby changing adistance between the end caps, wherein the end caps and the one or moresidewalls enclose an inner chamber that is substantially evacuated, andwherein the end caps are connected such that the separation distancebetween the radiator and the reflector corresponds to the distancebetween the end caps.
 16. The aerial vehicle according to claim 12,further comprising a controller configured to: (i) determine thealtitude of the aerial vehicle, and (ii) cause the linkage to adjust theseparation distance between the radiator and the reflector based on thedetermined altitude.
 17. The aerial vehicle according to claim 12,wherein the linkage is further configured to dynamically adjust theseparation distance between the radiator and the reflector by: (i)reducing the separation distance responsive to an increase in altitudeof the aerial vehicle, and (ii) increasing the separation distanceresponsive to a decrease in altitude of the aerial vehicle.
 18. A methodcomprising: emitting radiation from an antenna configured to be mountedto a payload of an associated aerial vehicle, wherein the antenna has anemission pattern determined at least in part by a separation distancebetween a radiator and a reflector of the antenna, and wherein theantenna is configured to be situated such that the emission pattern isdirected in a ground-facing direction while the associated aerialvehicle is aloft and the antenna is mounted to the payload; decreasingthe separation distance between the radiator and the reflectorresponsive to a decrease in altitude of the associated aerial vehicle;and increasing the separation distance between the radiator and thereflector responsive to an increase in altitude of the associated aerialvehicle.
 19. The method according to claim 18, further comprising:determining the altitude of the associated aerial vehicle; and causingthe linkage to adjust the separation distance between the radiator andthe reflector based on the determined altitude.
 20. The method accordingto claim 18, wherein the linkage includes a vessel arranged such that achange in volume of the vessel causes a corresponding change in theseparation distance between the radiator and the reflector; and whereinthe vessel is configured such that the volume of the vessel is based onambient pressure, thereby causing the separation distance to be based,at least in part, on the ambient pressure.